Abstract: Apparatus for controlling multi-rotor vehicle vibrations and related methods are disclosed herein. An example apparatus includes a vibration level detector to determine a vibration level of a frame of a vehicle based on data received from a sensor of the vehicle, the vehicle including a rotor. The apparatus includes a rotor operation analyzer to determine an operational parameter of the rotor based on the vibration level. The apparatus includes a communicator to transmit an instruction including the operational parameter to a controller of the rotor.

Abstract: A method, apparatus, system, and computer program product for estimating material properties. Training data comprising results of testing samples for a set of materials over a range of loads applied to the samples is identified by a computer system. A machine learning model is trained by the computer system to output the material properties for materials in structures using the training data.

Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. Each ECS is configured as an integrated flight computer and motor controller.

Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. The ECSs are configured according to a model in which any of the ECSs is selectable as a primary ECS, and others of the ECSs are operable as secondary ECSs, the secondary ECSs configured to communicate respective rotor status information to the primary ECS, and the primary ECS configured to provide the motor commands to the secondary ECSs.

Abstract: A method, apparatus, system, and computer program product for estimating material properties. Training data comprising results of testing samples for a set of materials over a range of loads applied to the samples is identified by a computer system. A machine learning model is trained by the computer system to output the material properties for materials in structures using the training data.

Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. The ECSs are configured according to a model in which any of the ECSs is selectable as a primary ECS, and others of the ECSs are operable as secondary ECSs, the secondary ECSs configured to communicate respective rotor status information to the primary ECS, and the primary ECS configured to provide the motor commands to the secondary ECSs.

Abstract: A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. Each ECS is configured as an integrated flight computer and motor controller.

Abstract: A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

Abstract: Apparatus for controlling multi-rotor vehicle vibrations and related methods are disclosed herein. An example apparatus includes a vibration level detector to determine a vibration level of a frame of a vehicle based on data received from a sensor of the vehicle, the vehicle including a rotor. The apparatus includes a rotor operation analyzer to determine an operational parameter of the rotor based on the vibration level. The apparatus includes a communicator to transmit an instruction including the operational parameter to a controller of the rotor.

Abstract: A multi-functional composite structure has a modular design that can be altered depending on an extreme environment in which the structure will be exposed such as hazardous radiation, micro-meteoroid and orbital debris impacts, extreme temperature changes, etc. The material combinations employed in the multi-functional composite structure provide a supporting structure with low weight and maximum protection from radiation, debris impacts and temperature variations.

Abstract: An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.

Abstract: An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.

Abstract: A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

Abstract: A multi-functional composite structure has a modular design that can be altered depending on an extreme environment in which the structure will be exposed such as hazardous radiation, micro-meteoroid and orbital debris impacts, extreme temperature changes, etc. The material combinations employed in the multi-functional composite structure provide a supporting structure with low weight and maximum protection from radiation, debris impacts and temperature variations.

Abstract: A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

Abstract: A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

Abstract: A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

Abstract: A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

Abstract: A simple, inexpensive, and fast method of establishing if a defect does or does not exist within a thick-walled solid geometry, which is especially useful to detect if such a defect, a crack, exists within a gun barrel. With further analysis, the method allows not only the identification of the defect's presence; but, a means of establishing the size thereof—which, for example, is critical to understanding if a gun tube has a defect that would warrant its being taken out of service for the safety of its crew or removed from manufacturing. The method involves creating an acoustic vibration in the particular thick-walled, solid geometry, esp. a gun barrel, and observing the vibration pattern which results.

Abstract: The present invention is a nondestructive and quantitative laser ultrasonic laser apparatus and associated method for determining adhesion quality of a coating on a substrate. The apparatus of the invention is preferably a pulsed laser for generation and Michelson-type interferometer based system and includes a rotary probe head assembly for making evaluations within a cylindrical test specimen. The method of the invention includes data analysis that uses acquired data from the ultrasonic laser apparatus and computes the dispersion relation or curves (frequency versus velocity) using a ridge-following technique in wavelet analysis and from this, outputs the adhesive quality of the coating by comparing it with a theoretically based determination of a particular coating/substrate bond system. The invention is used for evaluating adhesion quality of coatings used in a gun bore.